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为了提高吸气式高超声速飞行器绕流的求解效率,采用空间推进求解抛物化PNS(parabolizedNavier-Stokes)方程和时间迭代求解Navier-Stokes(N-S)方程的混合计算流体动力学(CFD)方法来求解高超声速飞行器整机绕流.在超声速占主导的流动区域采用空间推进求解抛物化N-S方程的方法,在亚声速和分离区采用时间迭代求解N-S方程的方法.对于求解二维带化学反应的吸气式高超声速飞行器绕流,混合CFD方法和完全时间迭代方法相比,可得到同等准确的数值模拟结果,并且求解效率提高了数倍.
In order to improve the solution efficiency of the aspirated hypersonic vehicle, a hybrid computational fluid dynamics (CFD) method for solving parabolicized Navier-Stokes equations and time-iterative Navier-Stokes equations is proposed. Hypersonic aircraft flow around the flow in the supersonic flow region dominated by the use of space to promote the parabolic NS equation method, the sub-sonic and separation region using time iterative method for solving the NS equation for solving two-dimensional chemical reaction with suction Compared with the full time iteration method, the CFD method and the CFD method can obtain the same accurate numerical simulation results and improve the solution efficiency several times.